EP0340149B1 - Staubabscheider für eine luftgekühlte Schaufel - Google Patents

Staubabscheider für eine luftgekühlte Schaufel Download PDF

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Publication number
EP0340149B1
EP0340149B1 EP89630081A EP89630081A EP0340149B1 EP 0340149 B1 EP0340149 B1 EP 0340149B1 EP 89630081 A EP89630081 A EP 89630081A EP 89630081 A EP89630081 A EP 89630081A EP 0340149 B1 EP0340149 B1 EP 0340149B1
Authority
EP
European Patent Office
Prior art keywords
blade
dirt
air
section
inlet
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP89630081A
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English (en)
French (fr)
Other versions
EP0340149A1 (de
Inventor
Kenneth B. Hall
Thomas A. Auxier
Wesley D. Brown
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US07/185,227 external-priority patent/US4820122A/en
Priority claimed from US07/185,226 external-priority patent/US4820123A/en
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP0340149A1 publication Critical patent/EP0340149A1/de
Application granted granted Critical
Publication of EP0340149B1 publication Critical patent/EP0340149B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to cooled blades of a rotor of a gas turbine engine and particularly for controlling foreign matter contained in the cooling air so as to prevent clogging of the cooling air holes or passages in the blade.
  • the object of the invention is to obviate the problems enumerated in the above by designing the blade itself to carry its own dirt removal system, hence providing a method to make the cooled turbine blades tolerant to dirt or dust contaminating the cooling air.
  • a feature of one embodiment of the invention is to cast the aircraft turbine engine multipassage blade with internal baffles such that the baffles guide the entrained dirt into a preselected passage internally of the blade where the velocity of the cooling air in that passage carries the entrained dirt to a dirt removal hole formed in the tip of the blade.
  • a stamped out sheet metal deflector or baffle is attached to the root of the blade so as to direct the dirt entrained air either into a high velocity passage in the blade itself or a high velocity passage in the turbine disk or in proximity thereto.
  • the baffle can be stamped out from a sheet metal stock and can be sized to attach the deflector as a "fix" to the underside of existing blades.
  • the turbine blade of the invention eliminates the need of the upstream air cleansing schemes that have been heretofore prevalent in the gas turbine engine technology.
  • Fig. 1 is a view partly in section and schematic illustrating a prior art air cooled turbine blade design.
  • Fig. 2 is a view similar to Fig. 1 of an air cooled turbine blade according to one embodiment of the present invention.
  • Fig. 3 is a partial view of a turbine rotor in section and partly in schematic incorporating a turbine blade according to another embodiment of the present invention.
  • Fig. 4 is a partial view taken along the lines 4-4 of Fig. 3.
  • Fig. 5 is a bottom view of the blade of Fig. 3 showing the deflectors fabricated from sheet metal stock.
  • Fig. 6 is a partial view similar to Fig. 3 showing modification of the embodiment of Fig. 3.
  • Fig. 7 is a view in elevation of the stamped out sheet metal stock forming the deflector of Fig. 6.
  • the internal construction of the blade may utilize any of the heat transfer enhancement schemes that are known in this technology.
  • the airfoil would incorporate the requisite trip strips, pedestals, vanes and the like to achieve the desired cooling.
  • Fig. 1 The prior art design is illustrated in Fig. 1 showing the interior of the airfoil section taking a section through the longitudinal or spanwise axis.
  • the airfoil section 10 of the blade is partitioned by a plurality of ribs into a plurality of subpassages.
  • the blade comprises the leading edge 12, trailing edge 14, tip 16 and root end 18.
  • Ribs 20,22 and 24 define four passages 26, 28, 30 and 32 extending in the spanwise direction
  • rib 20 is bifurcated defining additional subpassages for defining serpentine passages with rib 30.
  • each of the passages and the impingement sections are designed to accomplish well defined objectives, which are not dealt with in this patent application.
  • the design of these high technology cooled turbine blades require a significant number of holes which also have well defined objectives.
  • the ribs are modified in such a manner as to form deflectors for the dirt entrained cooling air so that all or a significant amount of the dirt entrained air is directed to the trailing edge passage 36; the passages being rearranged to provide for the dirt removal.
  • rib portions 40, 42 and 44 are disposed at the root portion of the blade in proximity to the inlet of passages 26a, 28a and 30a and as noted are inclined from the root to the tip and extend in the chord direction and are cast into the blade. These rib portions 40, 42 and 44 serve to deflect the cooling air entrained with dirt in a direction toward the trailing edge passage 36.
  • Passage 36 is specifically designed as a straight through passage and is directly communicating with the inlet air admitted into the root in passage 46.
  • a dirt removal hole 48 is formed at the tip end of passage 36 to discharge the dirt entrained air into the engine's gas path. The purpose of designing passage 36 with as little, if any, turns is to assure that the velocity of the cooling airstream is sufficient to flow the dirt directly out through the dirt removal hole 48.
  • the other passages 26a, 28a and 30a are thus substantially free of dirt.
  • a dirt removal system directly in the blade, by selectively directing the dirt through the passage with the high velocity cooling airstream, it is now possible to eliminate the many purge holes that heretofore have been designed with these blades. This obviates the problem of utilizing a large amount of air that is not being utilized solely for cooling and as experience has shown, the air velocity in some of these passages associated with the purge air holes is relatively low which impedes or limits the removal of dirt.
  • the airfoil section 10 of the blade of Fig. 3 is partitioned by a plurality of ribs 20, 22, 24 into a plurality of subpassages.
  • the blade comprises the leading edge 12, trailing edge 14, tip 16 and root end 18.
  • Ribs 20, 22 and 24 define multi passages including passage 56 and 58 extending in the spanwise direction.
  • deflecting members 50 are mounted to the root end of the blade and serve to deflect the dirt entrained air to one or more specific passageways.
  • the deflectors 50 are stamped out of sheet metal blank 52 and then is suitably attached to the root of the blade 10 by any well-known method such as brazing, welding, etc.
  • the deflectors 50 which are defined by raised panels extending from the leading edge to the trailing edge and are positioned to overlie the passages intended to be protected. The dimensions of these panels will be predicated on the size of the opening being protected. In this instance, the deflectors 50 deflect the dirt entrained cooling air into the trailing edge passage 56 and leading edge passage 58 and divert this contaminated air from the serpentine passages.
  • the leading edge passage 58 and trailing edge passage 56 are formed so as to afford as little pressure losses as possible and receive air at sufficient velocity to carry the dirt to the dirt removal holes 60. The dirt free or substantially dirt free air can still get into the serpentine passages through the openings underneath the panels 50.
  • Figs. 6 and 7 illustrate a third embodiment of this invention utilizing a similar fabricated deflector where the dirt entrained air is directed to the high velocity passageway 70 and discharged away from the blade's internal passageways through apertures 72 formed in the blade or in the disk 74 of the turbine rotor.
  • the deflectors 76 are stamped out of a sheet metal stock 78 which is sized to overlie the passages at the root of the turbine blade.
  • the sheet metal plate 78 can be affixed to the blade in any suitable manner, by say brazing, welding or mechanical attaching means.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (6)

  1. Innengekühlte Laufschaufel für ein Gasturbinentriebwerk, wobei die Laufschaufel einen Fußabschnitt und einen Spitzenabschnitt hat, eine Wandeinrichtung zwischen dem Fußabschnitt und dem Spitzenabschnitt, welche das Schaufelblatt der Laufschaufel bildet, und mehrere Rippen, die Durchlässe (26a, 28a, 30a) bilden, welche sich in Richtung der Spannweite in der Laufschaufel erstrecken, um Kühlluft durch die Laufschaufel hindurchzuleiten und in den Gasweg des Turbinentriebwerks über Öffnungen abzugeben, die in dem Schaufelblatt gebildet sind, gekennzeichnet durch eine Einrichtung, die Schmutz daran hindert, die Öffnungen zu verstopfen, wobei die Einrichtung wenigstens einen geraden Durchlaß (36) und ein in dem Spitzenabschnitt gebildetes Loch (48) aufweist, das für das größte Schmutzpartikel bemessen ist, welches erwartungsgemäß in der Kühlluft mitgeführt wird, und wenigstens eine Rippe (40) in dem Fußabschnitt, die einen leitwandartig geformten Teil hat, der relativ zu den Durchlässen (26a, 28a, 30a) abgewinkelt angeordnet ist, um die schmutzhaltige Luft in den geraden Durchlaß (36) zu leiten und zu verhindern, daß die schmutzhaltige Luft in die anderen Durchlässe (26a, 28a, 30a) gelangt.
  2. Innengekühlte Laufschaufel nach Anspruch 1, dadurch gekennzeichnet, daß der Fuß der Laufschaufel zusätzliche Rippen (42, 44) aufweist, die relativ zu dem Eingang der Durchlässe (26a, 28a, 30a) abgewinkelt angeordnet und von diesen beabstandet sind, wobei wenigstens eine der Rippen (40, 42, 44) ein Teil der Wand ist, die wenigstens einen der Durchlässe (26a, 28a, 30a) begrenzt.
  3. Innengekühlte Turbinenlaufschaufel, die zur Befestigung in einer Turbinenscheibe (74) vorgesehen ist, für ein Gasturbinentriebwerk, wobei die Laufschaufel einen Fußabschnitt zum Befestigen der Laufschaufel in einer in der Scheibe (74) gebildeten Ausnehmung (70) und einen Spitzenabschnitt hat, eine Wandeinrichtung zwischen dem Fußabschnitt und dem Spitzenabschnitt, die ein Schaufelblatt (10) der Laufschaufel bildet, eine Einrichtung mit einem Einlaß innerhalb der Laufschaufel zum Leiten von Kühlluft durch den Einlaß in das Schaufelblatt (10) und zum Abgeben durch Öffnungen in der Wand in den Gasweg des Gasturbinentriebwerks, gekennzeichnet durch eine Einrichtung, die Schmutz daran hindert, die Öffnungen zu verstopfen, wobei die Einrichtung ein Blechteil (78) aufweist, das insgesamt rechteckförmig ist und einen Teil hat, der so ausgestanzt ist, daß es einen nach unten vorstehenden Ablenkteil (76) hat, welcher sich abgewinkelt von ihm aus erstreckt, wobei das Blechteil (78) an dem Fußabschnitt der Laufschaufel so befestigt ist, daß der Ablenkteil (76) relativ zu dem Einlaß abgewinkelt angeordnet ist und ihm überlagert ist, wodurch der Ablenkteil (76) die schmutzhaltige Luft von dem Einlaß weg- und zu einer Auslaßöffnung (72) für schmutzhaltige Luft lenkt, während er gleichzeitig relativ schmutzfreier Luft gestattet, durch Herumgehen um den durch den Ablenkteil (76) gebildeten Winkel in den Einlaß zu gelangen.
  4. Innengekühlte Turbinenlaufschaufel nach Anspruch 3, gekennzeichnet durch mehrere innere Durchlässe in der Turbinenlaufschaufel und mehrere Einlässe, die jedem inneren Durchlaß zugeordnet sind, einen komplementären Ablenkteil (76), der aus der Blechplatte (78) ausgestanzt und so ausgerichtet ist, daß er relativ zu jedem der mehreren Einlässe abgewinkelt angeordnet ist und den Einlässen überlagert ist, um den in dem Luftstrom mitgeführten Schmutz von dem Einlaß wegzulenken.
  5. Innengekühlte Laufschaufel für ein Gasturbinentriebwerk, wobei die Laufschaufel einen Fußabschnitt (18), einen Spitzenabschnitt (16) und eine Wandeinrichtung zwischen dem Spitzenteil und dem Fußabschnitt (18) hat, die ein Schaufelblatt (10) bildet, mehrere in Richtung der Spannweite angeordnete Rippen (20, 22, 24) innerhalb der Laufschaufel, die gewundene Durchlässe zum Hindurchleiten von Kühlluft durch die Laufschaufel und zum Abgeben derselben über Öffnungen in der Wandeinrichtung bilden, gekennzeichnet durch eine Schmutzentfernungseinrichtung, die wenigstens einen geraden Durchlaß (56, 58) innerhalb der Laufschaufel zum Leiten von Kühlluft von dem Fußabschnitt (18) zu dem Spitzenabschnitt und zum Abgeben über eine in dem Spitzenabschnitt (16) gebildete Öffnung (60) aufweist, wobei die Öffnung (60) so bemessen ist, daß das größte Schmutzpartikel hindurchtreten kann, das erwartungsgemäß in der Kühlluft mitgeführt wird, ein Blechteil (52), in welchem Ablenkteile (50) durch Stanzen gebildet sind, die sich relativ zu der in dem Blechteil (52) verbliebenen Öffnung abgewinkelt erstrecken, eine Einrichtung zum Befestigen des Blechteils (52) an dem Fußabschnitt (18) der Laufschaufel und zum Ausrichten der Ablenkteile (50), so daß sie über dem Einlaß der gewundenen Durchlässe liegen, und zum Lenken der schmutzhaltigen Luft in den geraden Durchlaß (56, 58).
  6. Innengekühlte Laufschaufel nach Anspruch 1 oder 5, dadurch gekennzeichnet, daß die Laufschaufel eine Turbinenlaufschaufel ist.
EP89630081A 1988-04-25 1989-04-20 Staubabscheider für eine luftgekühlte Schaufel Expired - Lifetime EP0340149B1 (de)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
US07/185,227 US4820122A (en) 1988-04-25 1988-04-25 Dirt removal means for air cooled blades
US185226 1988-04-25
US185227 1988-04-25
US07/185,226 US4820123A (en) 1988-04-25 1988-04-25 Dirt removal means for air cooled blades

Publications (2)

Publication Number Publication Date
EP0340149A1 EP0340149A1 (de) 1989-11-02
EP0340149B1 true EP0340149B1 (de) 1993-05-19

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EP89630081A Expired - Lifetime EP0340149B1 (de) 1988-04-25 1989-04-20 Staubabscheider für eine luftgekühlte Schaufel

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EP (1) EP0340149B1 (de)
JP (1) JP2877345B2 (de)
DE (1) DE68906594T2 (de)

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US6238183B1 (en) 1998-06-19 2001-05-29 Rolls-Royce Plc Cooling systems for gas turbine engine airfoil
US9915176B2 (en) 2014-05-29 2018-03-13 General Electric Company Shroud assembly for turbine engine
US10036319B2 (en) 2014-10-31 2018-07-31 General Electric Company Separator assembly for a gas turbine engine
US10082076B2 (en) 2014-05-07 2018-09-25 General Electric Company Ultra compact combustor having reduced air flow turns
US10167725B2 (en) 2014-10-31 2019-01-01 General Electric Company Engine component for a turbine engine
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US6238183B1 (en) 1998-06-19 2001-05-29 Rolls-Royce Plc Cooling systems for gas turbine engine airfoil
WO2000019065A1 (de) 1998-09-30 2000-04-06 Siemens Aktiengesellschaft Gasturbinenlaufschaufel und verfahren zur herstellung einer gasturbinenlaufschaufel
US10286407B2 (en) 2007-11-29 2019-05-14 General Electric Company Inertial separator
US11053844B2 (en) 2014-05-07 2021-07-06 General Electric Company Ultra compact combustor
US12312995B2 (en) 2014-05-07 2025-05-27 General Electric Company Ultra compact combustor
US10082076B2 (en) 2014-05-07 2018-09-25 General Electric Company Ultra compact combustor having reduced air flow turns
US9915176B2 (en) 2014-05-29 2018-03-13 General Electric Company Shroud assembly for turbine engine
US10167725B2 (en) 2014-10-31 2019-01-01 General Electric Company Engine component for a turbine engine
US10036319B2 (en) 2014-10-31 2018-07-31 General Electric Company Separator assembly for a gas turbine engine
US10704425B2 (en) 2016-07-14 2020-07-07 General Electric Company Assembly for a gas turbine engine
US11199111B2 (en) 2016-07-14 2021-12-14 General Electric Company Assembly for particle removal
US10823418B2 (en) 2017-03-02 2020-11-03 General Electric Company Gas turbine engine combustor comprising air inlet tubes arranged around the combustor

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JPH0223202A (ja) 1990-01-25
DE68906594T2 (de) 1993-08-26
EP0340149A1 (de) 1989-11-02
JP2877345B2 (ja) 1999-03-31
DE68906594D1 (de) 1993-06-24

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